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Flight, analog-simulator, and analytical studies of an automatically controlled interceptor which uses a bank-angle-error computer for lateral commands

Description: Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
Date: August 11, 1958
Creator: Cheatham, Donald C. & Brissenden, Roy F.
Partner: UNT Libraries Government Documents Department

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. 1.-swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lift and Drag, Mach Number, 1.61

Description: Supersonic store interference - 1, swept-wing heavy bomber with large stores - lift & drag at mach 1.61.
Date: March 11, 1955
Creator: Carlson, H. W. & Smith, N. F.
Partner: UNT Libraries Government Documents Department

Preliminary Results from Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor with an Annular-Piloted Baffle-Type Flameholder

Description: A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037. To promote combustion efficiency at such low fuel-air ratios, a divided-flow system was employed which bypassed a portion of the engine air around the combustion region. Three combustor lengths, three lengths of the shroud which separated the bypass air from the burning stream, and four fuel-distribution systems were investigated over a range of fuel-air ratios from 0.025 to 0.055 and a range of engine air flows from 40 to 110 pounds per second (combustor-outlet total pressures from 500 t o 1800 lb/sq ft abs). The highest efficiencies were obtained with a combustor length of 78 inches and a shroud length of 6 inches. At the lowest air flow, with combustor pressures of about 700 pounds per square foot absolute, a maximum efficiency of about 93 percent was obtained. The efficiency increased with combustor length, a typical increase being from 88 to 95 percent as the length increased from 60 to 96 inches. The length of the shroud separating the bypass air from the burning stream affected not only the efficiency level, but also the fuel-air ratio at which the maximum efficiency occurred. In general, a longer shroud caused the maximum efficiency to occur at lower f'uel-air ratios. Highest efficiencies usually resulted from the use of a fuel-injection system giving a uniform fuel profile. The efficiency at low fuel-air ratios could be considerably improved by the use of a radially nonuniform fuel profile which concentrated the fuel towards the outermost portion of the burning stream The total-pressure ratio across the combustor was about 0.86 at the ...
Date: May 11, 1955
Creator: Rayle, W. D.; Smith, I. D. & Wentworth, C. B.
Partner: UNT Libraries Government Documents Department

Drag and static stability at low lift of rocket-powered models of the Convair MX-1626 airplane at Mach numbers from 0.7 to 1.5

Description: Report presenting flight testing on models of the proposed Consolidated Vultee Aircraft Corporation MX-1626 airplane with nacelles and without nacelles. Results regarding drag level, design modifications, dampening, trimming, and the use of ventral boosters are provided.
Date: June 11, 1953
Creator: Hall, James R. & Hopko, Russell N.
Partner: UNT Libraries Government Documents Department

Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content

Description: Flight icing-rate data obtained in a dense and. abnormally deep supercooled stratiform cloud system indicated the existence of liquid-water contents generally exceeding values in amount and extent previously reported over the midwestern sections of the United States. Additional information obtained during descent through a part of the cloud system indicated liquid-water contents that significantly exceeded theoretical values, especially near the middle of the cloud layer.. The growth of cloud droplets to sizes that resulted in sedimentation from the upper portions of the cloud is considered to be a possible cause of the high water contents near the center of the cloud layer. Flight measurements of the vertical temperature distribution in the cloud layer indicated a rate of change of temperature with altitude exceeding that of the moist adiabatic lapse rate. This excessive rate of change is considered to have contributed to the severity of the condition.
Date: July 11, 1951
Creator: Perkins, Porter J. & Kline, Dwight B.
Partner: UNT Libraries Government Documents Department

Effect of pressure level on afterburner-wall temperatures

Description: Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. For a given ratio of cooling airflow to afterburner gas flow, the afterburner-wall temperature increased as afterburner-outlet pressure was increased. The results indicated that heat transfer by luminous radiation was not significant any pressure level investigated.
Date: June 11, 1958
Creator: Shillito, Thomas B. & Smolak, George R.
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Description: From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."
Date: August 11, 1958
Creator: Stoney, W. E., Jr.
Partner: UNT Libraries Government Documents Department

Flutter Tests of a 1/25-Scale Model of the B-36J/RF-84F Tip-Coupled Airplane Configuration in the Langley 19-Foot Pressure Tunnel

Description: Report discussing tests of a model of a B-36J/RF-84F tip-coupled airplane to evaluate the flutter characteristics where bomber-body freedoms are allowed and to obtain information about the dynamic stability characteristics. The variables studied were the skew angle of the fighter-bomber coupling, the fighter longitudinal position, the fighter and bomber loading, angle of sideslip, degrees of body freedom, and number of fighters. Flutter was primarily found to occur when the fighter roll frequency was near the natural chordwise-bending frequency of the bomber wing.
Date: January 11, 1956
Creator: Neely, Robert H.
Partner: UNT Libraries Government Documents Department

An investigation of the low-speed stability and control characteristics of a 1/10-scale model of the McDonnell XF3H-1 airplane

Description: Report presenting an investigation of the low-speed, power-off stability and control characteristics of a model of the McDonnell XF3H-1 airplane. Flight testing occurred in the clean and slat- and flaps-extended conditions over a range of lift coefficients.
Date: October 11, 1951
Creator: Draper, John W.
Partner: UNT Libraries Government Documents Department

Preliminary analysis of a nuclear powered supersonic airplane using ramjet engines

Description: Report discussing performance estimates for several airplanes using General Electric AC-210 ramjet nuclear-powered engines. Assumptions used for designing the engines, radiation shield, and airframe are described. Potential tradeoffs in regards to power and weight reduction are also discussed.
Date: April 11, 1958
Creator: Weber, Richard J. & Connolley, Donald J.
Partner: UNT Libraries Government Documents Department

Stability of ballistic reentry bodies

Description: Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date: August 11, 1958
Creator: Bird, John D. & Reese, David E., Jr.
Partner: UNT Libraries Government Documents Department

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a weng, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4. A 1/10-scale steel-wing model of the missile was flown with modifications to the basic wing plan form consisting of leading-edge chord-extensions deflected 7 deg downward together with the forward 15 percent of the wing chord, and inboard trailing-edge flaps deflected 5 deg downward. In addition, the model had a static-pressure tube mounted at the tip of the vertical tail for position-error measurements and had a speed brake also mounted on the vertical tail to trim the model to positive lift coefficients and to permit determination of the trim and drag effectiveness of the brake. The data are uncorrected for the effects of wing elasticity, but experimental wing influence coefficients are presented.
Date: February 11, 1955
Creator: Arbic, R. G.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of a 1/6-scale model of the Bumblebee XPM missile at high subsonic speeds

Description: Report presenting an investigation of a model of the Bumblebee XPM missile to determine the causes of booster-fin failures for a range of Mach numbers and Reynolds numbers. The cause of fin failure was determined to be the launching shoes that caused the missiles to trim at increasingly negative angles of attack. Additional testing with wing spoilers and alternate booster fins was also conducted.
Date: December 11, 1950
Creator: Nelson, Warren H.
Partner: UNT Libraries Government Documents Department

Investigation at Mach number 1.91 of spreading characteristics of jet expanding from choked nozzles

Description: Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date: February 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department

Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance

Description: Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Date: October 11, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Partner: UNT Libraries Government Documents Department

Preliminary flight investigation of the wing-dropping tendency and lateral-control characteristics of a 35 degree swept-wing airplane at transonic Mach numbers

Description: Report presenting results from a preliminary flight investigation on a swept-wing airplane of the lateral-control characteristics and wing-dropping tendency encountered at high Mach numbers. Measurements of aileron and rudder-control effectiveness are presented and used with estimated damping-in-roll characteristics and data from steady sideslips to approximate the variation of effective dihedral with Mach number.
Date: September 11, 1950
Creator: Rathert, George A., Jr.; Rolls, L. Stewart; Winograd, Lee & Cooper, George E.
Partner: UNT Libraries Government Documents Department

Preliminary tests to determine the maximum lift of wings at supersonic speeds

Description: Report presenting the results of a test program in a supersonic tunnel to determine the maximum lift of wings operating at supersonic speeds. A variety of wing plan forms of several thickness distributions were tested at a range of Mach numbers, Reynolds numbers, and angles of attack. The lift results, drag results, and Schileren photographs are described.
Date: December 11, 1947
Creator: Gallagher, James J. & Mueller, James N.
Partner: UNT Libraries Government Documents Department

Preliminary flight investigation of the dynamic longitudinal-stability characteristics of a 35 degree swept-wing airplane

Description: Report presenting flight measurements of the dynamic longitudinal-stability characteristics of a 35 degree swept-wing airplane. The results indicated that a sharp reduction in damping at a Mach number of 0.92 with maximum damping occurred at Mach number of 0.88 and 0.94. Results regarding oscillation periods, damping coefficients, scatter, and number of cycles required for oscillations to damp to a certain amplitude are provided.
Date: December 11, 1950
Creator: Triplett, William C. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department

Full-scale investigation of a wing with the leading edge swept back 47.5 degrees and having circular-arc and finite-trailing-edge-thickness ailerons

Description: Report presenting an investigation to determine the aerodynamic characteristics of a wing with a leading sweptback edge at 47.5 degrees and a 20-percent-chord, 50-percent-span outboard aileron. The wing had symmetrical circular-arc airfoil sections and was tested with a circular-arc contour aileron and a flat-sided contour aileron with finite trailing-edge thickness. The longitudinal aerodynamic characteristics and aileron effectiveness are provided for both types of ailerons.
Date: March 11, 1949
Creator: Lange, Roy H.
Partner: UNT Libraries Government Documents Department